CN109587821B - Aircraft crew connection system and method - Google Patents

Aircraft crew connection system and method Download PDF

Info

Publication number
CN109587821B
CN109587821B CN201811127571.6A CN201811127571A CN109587821B CN 109587821 B CN109587821 B CN 109587821B CN 201811127571 A CN201811127571 A CN 201811127571A CN 109587821 B CN109587821 B CN 109587821B
Authority
CN
China
Prior art keywords
data
data interface
powered
interface device
transceiver
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
CN201811127571.6A
Other languages
Chinese (zh)
Other versions
CN109587821A (en
Inventor
史蒂文·J·阿维拉
安东尼奥·桑切斯
约翰·P·巴伦
丹尼尔·J·埃利斯
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Boeing Co
Original Assignee
Boeing Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Boeing Co filed Critical Boeing Co
Publication of CN109587821A publication Critical patent/CN109587821A/en
Application granted granted Critical
Publication of CN109587821B publication Critical patent/CN109587821B/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W76/00—Connection management
    • H04W76/10—Connection setup
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D47/00—Equipment not otherwise provided for
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B1/00—Details of transmission systems, not covered by a single one of groups H04B3/00 - H04B13/00; Details of transmission systems not characterised by the medium used for transmission
    • H04B1/38—Transceivers, i.e. devices in which transmitter and receiver form a structural unit and in which at least one part is used for functions of transmitting and receiving
    • H04B1/40—Circuits
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04B—TRANSMISSION
    • H04B7/00—Radio transmission systems, i.e. using radiation field
    • H04B7/14—Relay systems
    • H04B7/15—Active relay systems
    • H04B7/185—Space-based or airborne stations; Stations for satellite systems
    • H04B7/18502—Airborne stations
    • H04B7/18506—Communications with or from aircraft, i.e. aeronautical mobile service
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L63/00—Network architectures or network communication protocols for network security
    • H04L63/10—Network architectures or network communication protocols for network security for controlling access to devices or network resources
    • H04L63/105—Multiple levels of security
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04W—WIRELESS COMMUNICATION NETWORKS
    • H04W12/00—Security arrangements; Authentication; Protecting privacy or anonymity
    • H04W12/08—Access security
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J13/00—Circuit arrangements for providing remote indication of network conditions, e.g. an instantaneous record of the open or closed condition of each circuitbreaker in the network; Circuit arrangements for providing remote control of switching means in a power distribution network, e.g. switching in and out of current consumers by using a pulse code signal carried by the network
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02J—CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER; SYSTEMS FOR STORING ELECTRIC ENERGY
    • H02J3/00—Circuit arrangements for ac mains or ac distribution networks
    • H—ELECTRICITY
    • H04—ELECTRIC COMMUNICATION TECHNIQUE
    • H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
    • H04L67/00—Network arrangements or protocols for supporting network services or applications
    • H04L67/01—Protocols
    • H04L67/12—Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks

Abstract

The invention relates to a flight crew connection system and method. Systems and methods in accordance with one or more embodiments are provided for an aircraft flight crew secure communication path to a plurality of aircraft data domains. In one example, a system includes one or more data interface devices configured to communicate data. The power module is configured to provide power to the one or more data interface devices, and a switch coupled between the power module and each of the one or more data interface devices is configured to selectively provide power from the power module to at least one of the one or more data interface devices. The data transceiver is configured to be coupled to an external communication device, and a controller coupled between the one or more data interface devices and the data transceiver is configured to provide a data communication path between the selectively powered data interface device and the data transceiver for the external communication device.

Description

Aircraft crew connection system and method
Technical Field
One or more embodiments relate generally to aircraft systems and, more particularly, for example, to secure flight crew communication connections.
Background
In the field of aircraft flight crew secure communications, efforts are being made to improve access of flight crew to multi-level network communications security within an aircraft cockpit. For example, different data domains on an aircraft require different levels of network access security, and existing solutions that provide secure network access require complex multi-unit systems to meet network security requirements. Accordingly, there is a need for improved access to multiple secure and unsafe data fields provided by a flight crew within an aircraft cockpit.
Disclosure of Invention
Disclosed herein, in accordance with one or more embodiments, is a system and method for providing a connection of a flight crew to a plurality of data fields within an aircraft cockpit. In various embodiments, at least one of the one or more data interface devices, each coupled to a different data domain, is selectively powered and a dedicated data communication path is formed between the powered data interface device and a data transceiver for communicating with the aircraft crew communication device. It is possible to communicate only with the data fields coupled to the selectively powered data interface device. Network security is provided because other data domains coupled to unpowered data interface devices cannot communicate over the data communication path.
In one example, the first data interface device is coupled to an avionics device, wherein the avionics device provides aircraft control data and aircraft information data. The selective first powered data interface device is for physically isolating aircraft control data and aircraft information data over a data communication path between the powered first data interface device and the data transceiver for communication with the aircraft crew communication device.
In another example, the second data interface device is coupled to a non-avionics device, wherein the non-avionics device provides passenger information and entertainment data. The second selectively powered data interface device is for physically isolating passenger information and entertainment data and broadband internet access over a data communication path between the second powered data interface device and the data transceiver for communicating with the aircraft crew communication device.
In one embodiment, a system includes one or more data interface devices configured to communicate data; a power module configured to provide power to the one or more data interface devices; a switch coupled between the power module and each of the one or more data interface devices and configured to selectively provide power from the power module to at least one of the one or more data interface devices; a data transceiver configured to be coupled to an external communication device; and a controller coupled between the one or more data interface devices and the data transceiver and configured to provide a data communication path between the selectively powered data interface device and the data transceiver for the external communication device.
In another embodiment, a method includes selectively switching power from a power module to at least one of one or more data interface devices to selectively power the at least one data interface device; forming a data communication path between the selectively powered data interface device and the data transceiver; data is communicated between at least one selectively powered data interface device and a data transceiver for an external communication device.
The scope of the invention is defined by the claims, which are incorporated into this section by reference. Embodiments of the present invention, as well as additional advantages thereof, will be more fully understood by those skilled in the art upon consideration of the following detailed description of one or more embodiments. Reference will be made to the accompanying drawings, which will be briefly described first.
Drawings
FIG. 1 illustrates a diagram of an aircraft and flight crew connection system including various aircraft data fields and network interfaces, in accordance with one or more embodiments of the present disclosure.
Fig. 2 illustrates a block diagram of a flight crew connection system according to an embodiment of the present disclosure.
Fig. 3 illustrates various data fields within an aircraft fuselage according to an embodiment of the present disclosure.
Fig. 4 illustrates various functions of a flight crew connection system according to an embodiment of the present disclosure.
Fig. 5 illustrates a panel concept display for a flight crew connection system according to an embodiment of the present disclosure.
Fig. 6A-6B show flowcharts describing methods for using the aircraft crew connection system according to embodiments of the present disclosure.
Detailed Description
Systems and methods are provided according to one or more embodiments that provide a secure wireless data communication connection for a flight crew personal electronic device with various data domains integrated within an aircraft. In this regard, the flight crew connection system provides for seamless connection of flight crew electronics to various aircraft data fields having different levels of network access security without compromising security level requirements.
Fig. 1 shows a diagram of an aircraft 101 including a flight crew connection system 100, various aircraft data fields, a plurality of aircraft network interfaces, and aircraft devices connected to the network interfaces, in accordance with one or more embodiments of the present disclosure. Flight crew connection system 100 provides a secure wireless data communication path between cockpit 110 of aircraft 101 and various wired and wireless network protocols on-board and external to aircraft 101. For example, the flight crew connection system 100 communicates with avionics devices 102 on the aircraft 101 through a wired communication interface 113 (preferably via a secure aircraft protocol data bus such as ARINC 429 or ARINC 717). In some embodiments, the flight crew connection system 100 communicates with the non-avionics device 104 through an ethernet interface 115. In various embodiments, the flight crew connection system 100 wirelessly and securely connects components of avionics 102 and non-avionics 104 with the cockpit 110 via a secure wireless Wi-Fi network 103A-C. In some implementations, the wireless Wi-Fi networks 103A-C are proprietary IEEE 802.11 Service Set Identifiers (SSID) airlines for dedicated and secure use by flight crew personal electronic devices (e.g., such as flight crew personal electronic device 203 of fig. 2) within the cockpit 110. The aircraft 101 includes an aircraft power module 106 (e.g., a power source) for providing power to the flight crew connection system 100.
In some embodiments, the flight crew connection system 100 communicates wirelessly with the ground electronics 108 to provide secure wireless communication between the ground electronics 108 and the cockpit 110. In some embodiments, the ground electronics 108 is wirelessly connected to the aircraft 101 through an airline-specific secure IEEE802.11 wireless network connection 103C, although other wireless network interfaces are also possible, such as an airline-specific secure IEEE WiMAX 802.16 wireless network connection. For example, the flight crew may download predictive maintenance reports from the ground electronics 108 and other data reports regarding the aircraft 101 onto the flight crew electronics 203. In some embodiments, the flight crew connection system 100 provides a second secure wireless network 119 for secure communication between the personal electronic device 203 and an external cellular device (e.g., such as the external cellular device 237A of fig. 2).
In various embodiments, avionics 102 include electronics for aircraft information systems and aircraft control systems. In some embodiments, the electronics and circuitry of avionics device 102 are distributed throughout aircraft 101. In some implementations, the avionics device 102 provides flight information and aircraft control data. In various embodiments, the non-avionics 104 include electronics for the passenger information system as well as electronics and networks connected to the passenger personal electronic device. In some implementations, the non-avionics devices 104 provide aircraft maintenance data, aircraft operational performance data, and other less secure flight crew applications.
The aircraft 101 includes a plurality of connection protocols for connecting components of the avionics device 102 and the non-avionics device 104. In some implementations, the components of the non-avionics device 104 utilize Wi-Fi communication networks 105A-D to provide broadband Internet access to passengers within the aircraft cabin 107. Passengers connect their personal electronic devices (e.g., smart phones, tablets, notebooks) wirelessly to the broadband internet through broadband Ku/Ka band SATCOM antenna 109. As discussed herein, the flight crew connection system 100 provides a secure data link between the Wi-Fi communication networks 105A-D and the cockpit 110 for the flight crew individual's electronic device 203 to access the broadband internet without violating the advanced security requirements of the aircraft 101 avionics 102.
Fig. 2 illustrates a block diagram of a flight crew connection system 100 according to an embodiment of the present disclosure. The flight crew connection system 100 includes a controller 201 (e.g., a Media Access Controller (MAC)/baseband processor), input data transceivers 211A-B (e.g., data interface devices), a wireless data transceiver 213 (e.g., data transceivers such as Wi-Fi, bluetooth, and NFC transceivers and antennas), a power module 217, and a domain switch 223.
The aircraft crew connection system 100 includes a power switch 219 (e.g., a power switch) connected to the aircraft power module 106. In some implementations, the power switch 219 is implemented as a single pole single throw power switch that is connected to the aircraft power module 106 at a first terminal 219A and to the power module 217 at a second terminal 219B. In some implementations, the power switch 219 is manually controlled at a display panel (e.g., display panel 500 of fig. 5) to provide 115 volts AC,400Hz, to the power module 217 connected to terminal 219B. However, in other embodiments, other aircraft power module 106 voltages and frequencies are possible. In other embodiments, the power switch 219 is a solid state switch electrically controlled by an electrical signal provided at the display panel 500. In some embodiments, the indicator 225 is mounted on the display panel and is implemented as a Light Emitting Diode (LED). The indicator 225 emits light when the power module 217 is energized and provides power. In other embodiments, the indicator 225 is implemented as an audible signal or other type of indicator to inform the operator that the power module 217 is providing power. In some embodiments, the power module 217 provides power directly to the controller 201, the wireless data transceiver 213, the cellular transceiver 215 (e.g., cellular transceiver, SIM card, and antenna), the Universal Serial Bus (USB) controller 231, and the Secure Digital (SD) card controller 232.
In various embodiments, the power module 217 provides power to the domain switch 223. The domain switch 223 is implemented as a single pole double throw switch, with the input terminal 223C connected to the power module 217. The first output terminal 223A is connected to a first input data transceiver 211A (e.g., a first data interface device) at an input connection 221A to provide power to the first input data transceiver 211A. The second output terminal 223B is connected to a second input data transceiver 211B (e.g., a second data interface device) at an input connection 221B to provide power to the second input data transceiver 211B. In other embodiments, the domain switch 223 includes fewer or more output terminals connected to fewer or more input data transceivers 211. In yet another embodiment, the domain switch 223 is implemented as a solid state switch controlled by an electrical signal provided at the display panel 500. The configuration of the domain switch 223 (e.g., single pole double throw) prevents the first input data transceiver 211A and the second input data transceiver 211B from powering on simultaneously to provide physical isolation of data communicated from the first input data transceiver 211A and the second input data transceiver 211B on the data buses 228A-F.
The first input data transceiver 211A is connected to the avionics device 102 via the wired communication interface 113 and a data bus 221C. In some implementations, the data bus 221C is implemented as an aircraft-specific ARINC 429 data bus to supplement the wired communication interface 113. In other embodiments, the data bus 221C is implemented as an aircraft-specific ARINC 717 data bus to supplement the wired communication interface 113. In yet another embodiment, data bus 221C is implemented as an Ethernet data bus to supplement wired communication interface 113. While in another embodiment, the data bus 221C is implemented as an analog discrete signal to supplement the wired communication interface 113. In some implementations, the components of the avionics device 102 share one or more types of wired communication interface 113 implementations. In some implementations, the components of the avionics device 102 include a flight management computer, a display processor computer, a proximity sensor electronics unit, a flight data acquisition unit, and an on-board network system. In other implementations, fewer or more aircraft units are included in the avionics device 102.
In some implementations, the second input data transceiver 211B is connected to the non-avionics device 104 (e.g., a passenger Wi-Fi on-board/off-board connection system) through the ethernet interface 115 and a data bus 221D implemented as an ethernet data bus to supplement the ethernet interface 115. In some implementations, the various components of the non-avionics device 104 share the ethernet interface 115. For example, in some embodiments, the non-avionics device 104 includes components of passenger information and entertainment systems including on-board Wi-Fi networks 105A-105D (see fig. 1) to provide broadband internet connectivity for passenger personal electronic devices (e.g., smartphones, tablets, laptops, etc.) through a broadband Ku/Ka band SATCOM antenna 109.
The flight crew connection system 100 provides the capability of a secure data connection to an aircraft information system (e.g., as part of the avionics device 102) while also being able to provide a broadband internet connection via the non-avionics device 104 over a common data communication path. This is due to the domain switch 223 which provides physical power isolation for the avionics device 102 and the non-avionics device 104 when either the input data transceiver 211A or the input data transceiver 211B is selectively energized. For example, when the first input data transceiver 211A is powered on by controlling the domain switch 223, the first input data transceiver 211A communicates with the avionics device 102 to securely receive aircraft control data and aircraft information data. The first input data transceiver 211A provides aircraft control data and aircraft information data to the controller 201 via the data bus 228A.
In some embodiments, the controller 201 is implemented to provide a data communication path between the powered first input data transceiver 211A and the wireless data transceiver 213 via the data buses 228A and 228C. In other embodiments, the controller 201 is implemented to provide a data communication path between the powered first input data transceiver 211A and the USB controller 231 via the data buses 228A and 228E.
In some implementations, when the control domain switch 223 energizes the second input data transceiver 211B, the second input data transceiver 211B communicates with the non-avionics device 104 to receive passenger information and entertainment data. The second input data transceiver 211B provides passenger information and entertainment data to the controller 201 via the data bus 228B.
In some embodiments, the controller 201 is implemented to provide a data communication path between the powered second input data transceiver 211B and the wireless data transceiver 213 via the data buses 228B and 228C. In other embodiments, the controller 201 is implemented to provide a data communication path between the powered second input data transceiver 211B and the USB controller 231 via the data buses 228B and 228E.
When the first input data transceiver 211A device is powered on and the second input data transceiver 211B is powered off, the aircraft control data and the aircraft information data are physically isolated on the data communication paths 228A/228C and 228A/228E. In addition, broadband internet access and/or passenger information and entertainment data are physically isolated over data communication paths 228B/228C and 228B/228E when second input data transceiver 211B is powered on and first input data transceiver 211A is powered off. In some implementations, the controller 201 is configured to identify the selectively powered input data transceiver 211A/211B and communicate the identification to the personal electronic device 203 (e.g., an external communication device). In various embodiments, the security level of the personal electronic device 203 comprises a single or multiple layer security level, such as a biometric, pin, security badge, or other similar security feature, and the controller 201 is configured to verify the security level of the personal electronic device 203 (e.g., an external communication device).
In one embodiment, wireless data transceiver 213 is implemented with a secure Wi-Fi wireless network interface 213A to communicate between flight crew connection system 100 and flight crew personal electronic device 203. However, other secure wireless communication network interfaces are also possible, such as a secure near field wireless communication protocol 213B and/or a secure bluetooth wireless communication protocol 213C, or other secure wireless communication interfaces. In one embodiment, the flight crew personal electronic device 203 is a wireless smart device, such as a tablet computer, cellular device, or other portable smart device capable of secure wireless communication. The flight crew connection system 100 includes a proprietary and secure IEEE 802.11 service set identifier for airline-specific login only for the flight crew.
In one embodiment, USB controller 231 provides a wired universal serial bus interface between controller 201 and personal electronic device 203. For example, USB controller 231 is connected to controller 201 via data bus 228E and to personal electronic device 203 at USB communication adapter port 239 (e.g., a wired data communication port). Personal electronic device 203 includes a universal serial bus interface adapter (e.g., a wired communications adapter) to connect to adapter port 239. In this regard, the personal electronic device 203 communicates with the data transceiver 211A and/or the data transceiver 211B via a wired data communication path that includes the controller 201 and the USB controller 231. In some embodiments, USB controller 231 includes a charging adapter to charge personal electronic device 203 when connected to adapter port 239. The USB communication interface discussed herein presents one non-limiting embodiment of a wired data communication interface, and it should be understood that other wired data communication interfaces between the personal electronic device 203 and the flight crew connection system 100 are contemplated.
In one embodiment, the flight crew connection system 100 includes a Secure Digital (SD) card controller 232 to provide a Secure Digital (SD) card 235 (e.g., secure data storage card) interface. SD card controller 232 provides data communication between flight crew personal electronic device 203 and SD card 235. In this regard, the SD card controller 232 provides a communication interface to send and/or receive data between the personal electronic device 203 and the SD card 235.
In one embodiment, cellular transceiver 215 provides a secure wireless communication interface between personal electronic device 203 and cellular communication tower 237. In some implementations, the cellular transceiver 215 includes a Subscriber Identity Module (SIM) 241 to securely store the user identity of the personal electronic device 203. In this regard, the cellular transceiver 215 provides a second secure wireless network 119 for secure communications between the personal electronic device 203 and the external cellular device 237A. For example, in some implementations, application software is provided from an operator at a remote location via the second secure wireless network 119 to upload (e.g., such as to an existing flight operations software update) the flight operations software to one or more of the avionics device 102 LRUs (such as a Flight Management Computer (FMC)). In this regard, the flight operations software includes a unique identifier within the software title (header) to identify a particular LRU associated with the software, and the software is manually or automatically loaded into the LRU. In various embodiments, avionics device 102 provides discrete signals to cellular transceiver 215 to disable communications between personal electronic device 203 and external cellular device 237A while aircraft 101 is in the air.
Fig. 3 illustrates various data fields within an aircraft fuselage 301 according to an embodiment of the present disclosure. As shown in fig. 3, the aircraft fuselage 301 includes a plurality of aircraft data fields. For example, in some embodiments, fuselage 301 includes an aircraft control domain 312, an aircraft information system domain 314, a passenger information and entertainment system domain 316, and passenger owned device domains 318A-B.
In various embodiments, aircraft rules require separating direct access between one or more of the domains. For example, the aircraft control domain 312 and the aircraft information system domain 314 require direct Ethernet connections to be isolated from the passenger information and entertainment system domain 316 and the passenger owned device domains 318A-B. In various embodiments, the aircraft crew connection system 100 provides flight crew member specific and secure wireless access to one or more of the cockpit 110 by physically isolating the aircraft control domain 312 and/or the aircraft information system domain 314 from the passenger information and entertainment system domain 316 and/or the passenger owned device domains 318A-B.
In some implementations, the avionics device 102 includes a Flight Management Computer (FMC), a flight data acquisition unit (DFDAU), a Display Processing Computer (DPC), a Proximity Sensor Electronics Unit (PSEU), an Electronic Flight Bag (EFB), a Cabin Connectivity System (CCS), and an on-board network system (ONS). This list is not exhaustive and in other embodiments, fewer or more units (e.g., line Replaceable Units (LRUs)) may be included in avionics device 102. In some implementations, the non-avionics devices 104 include an on-board entertainment and connectivity system (IFEC) that communicates with a passenger-owned device domain 318 through less secure Wireless Access Points (WAPs) 105A-D within the aircraft cabin 107. The list of non-avionics devices 104 and/or non-avionics devices is not exhaustive and, in other implementations, may include fewer or more units and/or features.
Fig. 4 illustrates various functions of the aircraft crew connection system 100 according to an embodiment of the present disclosure. As shown, the aircraft crew connection system 100 provides flight crew member specific and secure wireless access to many of the functions included within the domains 312, 314, 316, and 318 of the aircraft 101.
For example, in some embodiments, crew wireless function 422 provides a dedicated Wi-Fi network for data access by personal electronic device 203 within aircraft 101 for flight crew use only. The wireless maintenance function 424 provides maintenance and troubleshooting data for aircraft systems to flight crew members via the flight crew specific Wi-Fi networks 103A-C. The wireless data download function 426 provides for downloading aircraft and maintenance data from the avionics device 102 (such as ONS and DFDAU) to the flight crew's personal electronic device 203. In some embodiments, the wireless data upload function 428 provides for the upload of flight plan information to the FMC and other data or information from the flight crew's personal electronic device 203 to the various avionics devices 102.
In some embodiments, the wired data up/down function 430 provides a high-speed wired USB connection for the flight crew's personal electronic device 203 for uploading and downloading tasks, and provides for quick charging of the personal electronic device 203 connected to the adapter port 239 of the USB controller 231. In some embodiments, secure high-speed/broadband link 432 provides a dedicated and secure high-speed off-board link to flight crew's personal electronic device 203 for downloading and uploading traffic and/or operational data. For example, the flight crew's personal electronic device 203 may be used to access weather data in anticipation of optimizing the flight path of the aircraft 101.
In some embodiments, the cellular data function 434 provides an alternative secure high-speed off-board link to the flight crew for downloading and uploading operational and business data and loadable software, such as application software for business and/or flight operations that may be loaded into the personal electronic device 203. When the aircraft is flying in the air, the cellular link is disabled to meet regulatory requirements. Wi-Fi data function 436 provides an alternative secure high-speed off-board link to the flight crew's personal electronic device 203 for downloading and uploading business and operational data. The network security function 438 is implicit by exclusive access to the aircraft control domain 312, the aircraft information system domain 314, the passenger information and entertainment system domain 316 via the domain switch 223. Secure memory module 440 provides localized storage of operational data via secure digital card 235. In some implementations, additional features may include near field 213B and/or bluetooth 213C wireless communication protocols for communication between the flight crew connection system 100 and the personal electronic device 203.
Fig. 5 illustrates a panel concept display (or display panel) 500 for the aircraft crew connection system 100 according to an embodiment of the present disclosure. For example, in some embodiments, the aircraft crew connection system 100 is in a form suitable for installation in a panel within the cockpit 110. In this regard, the aircraft crew connection system 100 is intended to meet cockpit-specific criteria such as: switch type, switch position, lights, color, font, and symbol. For example, the flight crew connection system 100 is activated with an ON/OFF switch 540 to enable or disable the system to broadcast its secure wireless signals, such as Wi-Fi wireless signals from the wireless data transceiver 213. In some embodiments, the display panel 500 includes an indicator light 225, implemented as a Light Emitting Diode (LED), for visual indication that the system is turned on and transmitting. In other embodiments, the indicator 225 is implemented as an audible signal or other type of indicator to inform the operator that the system is turned on and transmitting. Another feature includes a multi-position switch to select between avionics switch position 542 and IFEC switch position 544. The first switch position 540 will shut down the flight crew connection system 100 to meet rules that may require shut down of non-flight critical devices in an emergency situation. Avionics switch position 542 (highest security level) enables linking to aircraft avionics 102 data, but does not allow flight crew access to non-avionics 104 (such as a broadband SATCOM system). The IFEC switch position 544 (lowest security level) enables the flight crew to access the IFEC to connect to broadband internet applications and does not allow the flight crew to access the avionics device 102.
For example, in some embodiments, the fourth switch position is mounted and implemented by a rotary type switch. The fourth switch position is used to load an aircraft control computer, such as to wirelessly upload a flight plan from the personal electronic device 203 to the FMC. In various embodiments, the fourth switch position is isolated from other switch positions (e.g., switch positions 542 and/or 544) linked to avionics device 102 data and IFEC. In some embodiments, USB adapter port 239 mounts a wired data connection to provide a wired connection between flight crew connection system 100 and personal electronic device 203. In some embodiments, adapter port 239 is used to charge personal electronic device 203. In some embodiments, the flight crew connection system 100 includes a cellular transceiver 215 including, for example, a 3g/4g cellular modem and a SIM card 241 to allow the personal electronic device 203 to communicate with the cellular mobile device via the cellular tower 237 when the aircraft 101 is on the ground.
Fig. 6A-6B show flowcharts describing methods for using the aircraft crew connection system 100 according to embodiments of the present disclosure.
In block 601, the aircraft crew connection system 100 is powered on. In this regard, the switch 540 on the display panel 500 is used to switch power to the aircraft crew connection system 100. The switch 540 on the display panel 500 controls the power switch 219 connected between the aircraft power module 106 and the flight crew connection system 100 to power on and off the flight crew connection system 100.
In block 603, after power-up, the flight crew connection system 100 forms a wireless communication connection between the data transceiver 213 and the personal electronic device 203 (e.g., an external communication device). In some implementations, the secure Wi-Fi wireless interface 213A serves as a wireless connection between the flight crew connection system 100 and the flight crew personal electronic device 203. However, other secure wireless communication connections are also possible, such as a secure near field wireless communication connection 213B and/or a secure bluetooth wireless communication connection 213C. In some embodiments, the flight crew connection system 100 includes a proprietary and secure IEEE 802.11 service set identifier for airline-specific login only for the flight crew.
In block 605, a flight crew determines whether to communicate with the avionics device 102 or the non-avionics device 104. In this regard, the flight crew selects the avionics switch position 542 on the display panel 500 to communicate with the avionics device 102 or the IFEC switch position 544 to communicate with the non-avionics device 104.
In block 607, if the flight crew member selects the avionics switch position 542, the domain switch 223 is moved to the first output terminal 223A to switch power to a first data transceiver 211A (e.g., a first data interface device) coupled to the avionics device 102. The powered data transceiver 211A receives data from the avionics device 102 via a data bus 221C, the data bus 221C being implemented as an aircraft-specific ARINC 429 data bus, an aircraft-specific ARINC 717 data bus, and/or an ethernet interface. As discussed herein, the data transceiver 211A may communicate with one or more units associated with the avionics device 102.
In block 609, the controller 201 forms a secure data communication path between the data transceiver 211A (e.g., the first data interface device) and the data transceiver 213 via the data buses 228A and 228C. For example, the domain switch 223 isolates power only to the data transceiver 211A while maintaining the data transceiver 211B in an off state. Thus, communication between the data transceiver 211A and the avionics device 102 is isolated over the data bus within the flight crew connection system 100.
In block 611, the flight crew connection system 100 provides one or more units associated with the avionics device 102 to securely communicate avionics data between the data transceiver 211A (e.g., a first data interface device) and the data transceiver 213 for the personal electronic device 203 (e.g., an external communication device). In this regard, the avionics device 102 is physically isolated over the data buses 228A and 228C, and the wireless communication connection between the data transceiver 211A and the personal electronic device 203 is a proprietary IEEE 802.11 Service Set Identifier (SSID) airline-specific login for the flight-crew personal electronic device 203 only.
In block 613, the flight crew selects the IFEC switch position 544 on the display panel 500 to communicate with the non-avionics device 104.
In block 615, if the flight crew member selects the IFEC switch position 544, the domain switch 223 is moved to the second output terminal 223B to switch power to the data transceiver 211B (e.g., second data interface device) coupled to the non-avionics device 104. The powered data transceiver 211B receives data from the non-avionics device 104 via a data bus 221D implemented as an ethernet data bus to supplement the ethernet interface 115.
In block 617, the controller 201 forms a secure data communication path between the data transceiver 211B (e.g., the second data interface device) and the data transceiver 213 via the data buses 228B and 228C. As discussed herein, the domain switch 223 only isolates power to the data transceiver 211B while maintaining the data transceiver 211A in an off state. Thus, communication between the data transceiver 211B and the non-avionics device 104 is isolated over the data bus within the flight crew connection system 100. In this regard, security is maintained for avionics devices 102 within the flight crew connection system 100.
In block 619, the flight crew connection system 100 provides one or more units associated with the non-avionics device 104 to securely communicate non-avionics data between the data transceiver 211B (e.g., the second data interface device) and the data transceiver 213 for the personal electronic device 203 (e.g., the external communication device). In this regard, the non-avionics 104 are physically isolated over the data buses 228B and 228C, and the wireless communication connection between the data transceiver 211B and the personal electronic device 203 is a dedicated and secure IEEE 802.11 Service Set Identifier (SSID) airline-specific login for the flight-crew personal electronic device 203 only. For example, communication with the non-avionics device 104 enables flight crew members to access the broadband internet on their personal electronic device 203 and/or communicate with external cellular users.
Where applicable, the various embodiments provided by the present disclosure may be implemented using hardware, software, or a combination of hardware and software. Also where applicable, the various hardware components and/or software components set forth herein can be combined into composite components comprising software, hardware, and/or both without departing from the spirit of the present disclosure. Where applicable, the various hardware components and/or software components set forth herein can be separated into sub-components comprising software, hardware, or both without departing from the spirit of the present disclosure. Further, it is contemplated that software components may be implemented as hardware components, or vice versa, where applicable.
Software in accordance with the present disclosure (such as program code and/or data) may be stored on one or more computer readable media. It is also contemplated that the software identified herein may be implemented using one or more networked general-purpose or special-purpose computers and/or computer systems and/or in other ways. The order of the various steps described herein may be changed, combined into composite steps, and/or divided into sub-steps where applicable to provide the features described herein.
Furthermore, the present disclosure includes embodiments according to the following.
Item 1. A system comprising:
one or more data interface devices configured to communicate data;
a power module configured to provide power to one or more data interface devices;
a switch coupled between the power module and each of the one or more data interface devices and configured to selectively provide power from the power module to at least one of the one or more data interface devices;
a data transceiver configured to be coupled to an external communication device; and
a controller coupled between the one or more data interface devices and the data transceiver, and configured to provide a data communication path between the selectively powered data interface device and the data transceiver for the external communication device.
Item 2. The system of item 1, wherein the one or more data interface devices comprise:
a first data interface device configured to communicate with an avionics device when the first data interface device is powered, wherein the avionics device is configured to provide aircraft control data and aircraft information data; and
a second data interface device configured to communicate with the non-avionics device when the second data interface device is powered, wherein the non-avionics device is configured to provide broadband internet access and/or passenger information and entertainment data.
Item 3 the system of item 2, wherein the aircraft control data and the aircraft information data are physically isolated on the data communication path when the first data interface device is powered and the second data interface device is powered off, and wherein the broadband internet access and/or the passenger information and entertainment data are physically isolated on the data communication path when the second data interface device is powered and the first data interface device is powered off.
The system of any of clauses 2-3, wherein the data transceiver comprises a wireless data transceiver configured to provide a secure wireless communication network for the external communication device.
Item 5. The system of item 4, wherein the external communication device comprises one or more wireless smart devices configured to communicate with the wireless data transceiver via a secure wireless communication network.
The system of item 4, further comprising a cellular transceiver comprising a second secure wireless communication network configured to communicate between the one or more wireless smart devices and the external cellular device, wherein the second secure wireless communication network is configured to communicate application software including business and/or flight operations to the one or more wireless smart devices and/or avionics.
The system of any one of clauses 2 to 6, wherein the external communication device is configured to communicate data to the avionics via the data communication path when the first data interface device is powered, and wherein the avionics is configured to communicate flight information to the external communication device via the data communication path when the first data interface device is powered.
The system of any one of clauses 1 to 7, further comprising a universal serial bus controller coupled to the controller, the universal serial bus controller configured to provide a wired data communication path for an external communication device, wherein the external communication device comprises a wired communication adapter configured to couple to a universal serial bus controller data communication port to form the wired data communication path.
The system of item 8, wherein the universal serial bus controller further comprises a charging adapter configured to charge an external communication device coupled to the data communication port, and the system further comprises a secure digital card controller configured to communicate between the secure data storage card and the external communication device to provide secure data storage within the secure data storage card.
Item 10. An aircraft comprising the system of item 1, wherein the aircraft comprises:
avionics equipment;
a non-avionics device;
a power supply configured to provide power;
a power switch is coupled between the power source and the power module, the power switch configured to selectively switch power from the power source to the power module.
Item 11. A method of using the system of item 2, the method comprising the steps of:
selectively switching power from the power module to at least one of the one or more first data interface devices and the second data interface device;
coupling the first data interface device to the avionics equipment when the first data interface device is powered;
coupling the second data interface device to the non-avionics equipment when the second data interface device is powered;
forming a data communication path between the powered data interface device and the data transceiver;
verifying a security level of the external communication device; and
data is communicated between the powered data interface device and a data transceiver for an external communication device.
Item 12. A method of incorporating the system of item 1 into an aircraft, the method comprising the steps of:
Installing one or more data interface devices, a power module, a controller, and a data transceiver, wherein the controller is coupled between the one or more data interface devices and the data transceiver; and
a switch is coupled between the power module and each of the one or more data interface devices.
Item 13. A method comprising:
selectively switching power from the power module to at least one of the one or more data interface devices to selectively power the at least one data interface device;
forming a data communication path between the selectively powered data interface device and the data transceiver; and
data is communicated between the selectively powered data interface device and a data transceiver for an external communication device.
Item 14. The method of item 13, wherein the one or more data interface devices comprise:
a first data interface device configured to communicate with an avionics device, wherein the avionics device is configured to provide aircraft control data and aircraft information data; and
a second data interface device configured to communicate with a non-avionics device, wherein the non-avionics device is configured to provide broadband internet access and/or passenger information and entertainment data, the method further comprising:
Identifying a selectively powered data interface device; and
the identified selectively powered data interface device is communicated to an external communication device.
Item 15. The method of item 14, wherein communicating data further comprises the steps of:
communicating data between the first data interface device and the avionics device when the first data interface device is powered; and
when the second data interface device is powered, data is communicated between the second data interface device and the non-avionics device.
The method of any one of items 14-15, further comprising:
physically isolating aircraft control data and aircraft information data over the data communication path when the first data interface device is powered and the second data interface device is powered down, and
the broadband internet access and/or passenger information and entertainment data are physically isolated over the data communication path when the second data interface device is powered and the first data interface device is powered down.
The method of any of claims 13 to 16, wherein the data transceiver comprises a wireless data transceiver, and wherein communicating the data further comprises forming a secure wireless communication network for the external communication device.
The method of item 17, wherein the external communication device comprises one or more wireless smart devices, and wherein communicating data further comprises communicating data between the one or more wireless smart devices and the wireless data transceiver via a secure wireless communication network.
The method of item 18, further comprising a cellular transceiver comprising a second secure wireless communication network coupled to the wireless data transceiver, wherein forming the data communication path further comprises forming a second data communication path between the one or more wireless smart devices and the external cellular device via the second secure wireless communication network, wherein the second secure wireless communication network is configured to communicate application software including business and/or flight operations to the one or more wireless smart devices and/or avionics equipment.
The method of any of claims 13-19, further comprising a universal serial bus controller configured to provide a wired communication path, wherein the external communication device comprises a wired communication adapter configured to couple to a data communication port of the universal serial bus controller, wherein communicating data further comprises communicating via the data communication port for the external communication device, and wherein the method further comprises charging the external communication device coupled to the universal serial bus controller via the data communication port, and communicating data between the secure data storage card and the external communication device to provide secure data storage within the secure data storage card.
The above embodiments illustrate but do not limit the invention. It should also be understood that many modifications and variations are possible in accordance with the principles of the present invention. Accordingly, the scope of the invention is limited only by the following claims.

Claims (14)

1. A flight crew connection system comprising:
two data interface devices configured to communicate data;
a power module configured to provide power to the two data interface devices;
a switch coupled between the power module and each of the two data interface devices, and configured to selectively provide the power from the power module to at least one of the two data interface devices;
a data transceiver configured to be coupled to an external communication device; and
a controller coupled between the two data interface devices and the data transceiver, and configured to provide a data communication path between a selectively powered data interface device and the data transceiver for the external communication device, wherein,
the two data interface devices include:
a first data interface device configured to communicate with an avionics device when the first data interface device is powered, wherein the avionics device is configured to provide aircraft control data and aircraft information data; and
A second data interface device configured to communicate with a non-avionics device when the second data interface device is powered, wherein the non-avionics device is configured to provide broadband internet access and/or passenger information and entertainment data; and wherein the first and second heat sinks are disposed,
the aircraft control data and the aircraft information data are physically isolated on the data communication path when the first data interface device is powered up and the second data interface device is powered down, and wherein the broadband internet access and/or the passenger information and entertainment data are physically isolated on the data communication path when the second data interface device is powered up and the first data interface device is powered down.
2. The system of claim 1, wherein the data transceiver comprises a wireless data transceiver configured to provide a secure wireless communication network for the external communication device.
3. The system of claim 2, wherein the external communication device comprises one or more wireless smart devices configured to communicate with the wireless data transceiver via the secure wireless communication network, and further comprising a cellular transceiver comprising a second secure wireless communication network configured to communicate between the one or more wireless smart devices and an external cellular device, wherein the second secure wireless communication network is configured to communicate application software including business and/or flight operations to the one or more wireless smart devices and/or the avionics.
4. The system of claim 1, wherein the external communication device is configured to communicate data to the avionics equipment via the data communication path when the first data interface device is powered, and wherein the avionics equipment is configured to communicate flight information to the external communication device via the data communication path when the first data interface device is powered.
5. The system of claim 1, further comprising a universal serial bus controller coupled to the controller, the universal serial bus controller configured to provide a wired data communication path for the external communication device, wherein the external communication device comprises a wired communication adapter configured to couple to a universal serial bus controller data communication port to form the wired data communication path.
6. The system of claim 5, wherein the universal serial bus controller further comprises a charging adapter configured to charge the external communication device coupled to the data communication port, and further comprising a secure digital card controller configured to communicate between a secure data storage card and the external communication device to provide secure data storage within the secure data storage card.
7. A method of using the system of claim 2, the method comprising the steps of:
selectively switching power from the power module to at least one of one or more first data interface devices and second data interface devices;
coupling the first data interface device to the avionics equipment when the first data interface device is powered;
coupling the second data interface device to the non-avionics equipment when the second data interface device is powered;
forming a data communication path between a powered data interface device and the data transceiver;
verifying a security level of the external communication device; and
data is communicated between a powered data interface device and a data transceiver for the external communication device.
8. A method of incorporating the system of claim 1 into an aircraft, the method comprising the steps of:
installing two data interface devices, a power module, a controller and a data transceiver, wherein the controller is coupled between the two data interface devices and the data transceiver; and
a switch is coupled between the power module and each of the two data interface devices.
9. A method of aircraft crew connection comprising the steps of:
selectively switching power from the power module to at least one of the two data interface devices to selectively power at least one of the data interface devices;
forming a data communication path between the selectively powered data interface device and a data transceiver; and
communicating data between the selectively powered data interface device and a data transceiver for an external communication device, wherein,
the two data interface devices include:
a first data interface device configured to communicate with an avionics device when the first data interface device is powered, wherein the avionics device is configured to provide aircraft control data and aircraft information data; and
a second data interface device configured to communicate with a non-avionics device when the second data interface device is powered, wherein the non-avionics device is configured to provide broadband internet access and/or passenger information and entertainment data; and wherein the first and second heat sinks are disposed,
the aircraft control data and the aircraft information data are physically isolated on the data communication path when the first data interface device is powered up and the second data interface device is powered down, and wherein the broadband internet access and/or the passenger information and entertainment data are physically isolated on the data communication path when the second data interface device is powered up and the first data interface device is powered down.
10. The method of claim 9, further comprising:
identifying a selectively powered data interface device; and
the identified selectively powered data interface device is communicated to the external communication device.
11. The method of claim 10, wherein communicating data further comprises:
communicating data between the first data interface device and the avionics device when the first data interface device is powered; and
when the second data interface device is powered, data is communicated between the second data interface device and the non-avionics equipment.
12. The method of any of claims 9 to 11, wherein the data transceiver comprises a wireless data transceiver, and wherein communicating data further comprises forming a secure wireless communication network for the external communication device.
13. The method of claim 12, wherein the external communication device comprises one or more wireless smart devices, and wherein communicating data further comprises communicating data between the one or more wireless smart devices and the wireless data transceiver via the secure wireless communication network, and further comprising a cellular transceiver comprising a second secure wireless communication network coupled to the wireless data transceiver, wherein forming the data communication path further comprises forming a second data communication path between the one or more wireless smart devices and an external cellular device via the second secure wireless communication network, wherein the second secure wireless communication network is configured to communicate application software including business and/or flight operations to the one or more wireless smart devices and/or avionics.
14. The method of any of claims 9 to 11, further comprising a universal serial bus controller configured to provide a wired communication path, wherein the external communication device comprises a wired communication adapter configured to couple to a universal serial bus controller data communication port, wherein communicating data further comprises communicating via the data communication port for the external communication device, and wherein the method further comprises charging the external communication device coupled to the universal serial bus controller via the data communication port, and the communicating further comprises communicating data between a secure data storage card and the external communication device to provide secure data storage within the secure data storage card.
CN201811127571.6A 2017-09-27 2018-09-26 Aircraft crew connection system and method Active CN109587821B (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US15/717,731 2017-09-27
US15/717,731 US10764753B2 (en) 2017-09-27 2017-09-27 Flight crew connectivity systems and methods

Publications (2)

Publication Number Publication Date
CN109587821A CN109587821A (en) 2019-04-05
CN109587821B true CN109587821B (en) 2023-06-27

Family

ID=63642641

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201811127571.6A Active CN109587821B (en) 2017-09-27 2018-09-26 Aircraft crew connection system and method

Country Status (7)

Country Link
US (1) US10764753B2 (en)
EP (1) EP3462636B1 (en)
JP (1) JP7267697B2 (en)
CN (1) CN109587821B (en)
AU (1) AU2018222959B2 (en)
BR (1) BR102018069470A2 (en)
CA (1) CA3017895C (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11190529B2 (en) * 2017-11-24 2021-11-30 Eric Edward Stuck Method and system for on-board cyber (information) security appliance and applications to detect, manage and optionally mitigate cyber security events and /or anomalies on aircraft networks
US11526282B2 (en) * 2020-02-03 2022-12-13 Panasonic Avionics Corporation Secure wireless dataloading using in-flight entertainment connectivity systems

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5123112A (en) * 1990-08-02 1992-06-16 Gte Airfone Incorporated Air-to-ground communication system
CN102622829A (en) * 2012-03-28 2012-08-01 中国民航大学 Service integration settlement system for ground power supply and air conditioner set of civil airport
US8676393B1 (en) * 2011-03-15 2014-03-18 Cisco Technology, Inc. Power discovery and allocation within a power sharing group
CN104038393A (en) * 2013-03-05 2014-09-10 波音公司 Aircraft data transmission modules
EP2945244A1 (en) * 2014-05-15 2015-11-18 Airbus Operations GmbH Power and data distribution module and method for power and data distribution in an airborne vehicle

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7908042B2 (en) 2001-02-13 2011-03-15 The Boeing Company Methods and apparatus for wireless upload and download of aircraft data
US20030032426A1 (en) * 2001-07-24 2003-02-13 Gilbert Jon S. Aircraft data and voice communications system and method
US20040235469A1 (en) * 2003-05-21 2004-11-25 Krug William P. High bandwidth open wired network
JP2005328280A (en) * 2004-05-13 2005-11-24 Canon Inc Data processor
US8776146B2 (en) * 2004-12-28 2014-07-08 Livetv, Llc Aircraft in-flight entertainment system including a distributed digital radio service and associated methods
JP2006217327A (en) * 2005-02-04 2006-08-17 Kddi Corp Radio communications device and communication system
US8341298B2 (en) * 2005-12-02 2012-12-25 The Boeing Company Scalable on-board open data network architecture
JP4899696B2 (en) * 2006-07-31 2012-03-21 富士通株式会社 Communication device, relay device, communication system, communication method, and communication program
US7804280B2 (en) * 2006-11-02 2010-09-28 Current Technologies, Llc Method and system for providing power factor correction in a power distribution system
FR2937487B1 (en) 2008-10-22 2010-11-26 Airbus France DEVICE AND METHOD FOR COMMUNICATION BETWEEN A PORTABLE COMPUTER SYSTEM AND AVIONIC EQUIPMENT
US8493906B1 (en) 2009-09-11 2013-07-23 Rockwell Collins, Inc. Wireless aircraft gateway with auxiliary battery power
US9334063B2 (en) 2012-09-10 2016-05-10 Rosemount Aerospace, Inc. Aircraft avionics tablet interface module
CN103024925B (en) * 2012-11-16 2016-08-24 深圳市多尼卡电子技术有限公司 Passenger plane WIFI system
US10065583B2 (en) 2015-10-08 2018-09-04 Gulfstream Aerospace Corporation Integrated power distribution, data network, and control architectures for a vehicle

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5123112A (en) * 1990-08-02 1992-06-16 Gte Airfone Incorporated Air-to-ground communication system
US8676393B1 (en) * 2011-03-15 2014-03-18 Cisco Technology, Inc. Power discovery and allocation within a power sharing group
CN102622829A (en) * 2012-03-28 2012-08-01 中国民航大学 Service integration settlement system for ground power supply and air conditioner set of civil airport
CN104038393A (en) * 2013-03-05 2014-09-10 波音公司 Aircraft data transmission modules
EP2945244A1 (en) * 2014-05-15 2015-11-18 Airbus Operations GmbH Power and data distribution module and method for power and data distribution in an airborne vehicle

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
"Feasibility Study on New Services and Markets Technology Enablers";3GPP;《3GPP TR 22.891 V1.1.0》;20151105;全文 *
小型无人机飞行控制器的硬件设计;刘歌群;《计算机测量与控制》;20030225(第02期);全文 *

Also Published As

Publication number Publication date
US10764753B2 (en) 2020-09-01
AU2018222959A1 (en) 2019-04-11
CN109587821A (en) 2019-04-05
CA3017895A1 (en) 2019-03-27
JP2019083509A (en) 2019-05-30
EP3462636A1 (en) 2019-04-03
AU2018222959B2 (en) 2023-02-16
BR102018069470A2 (en) 2019-04-16
US20190098506A1 (en) 2019-03-28
JP7267697B2 (en) 2023-05-02
CA3017895C (en) 2023-03-21
EP3462636B1 (en) 2020-05-13

Similar Documents

Publication Publication Date Title
US7957735B1 (en) System and method for associating a wireless mobile communications device with a specific vehicle
EP2893647B1 (en) Methods and systems for vehicle broadband connection to a data network
CN105160505A (en) Unmanned aerial vehicle logistics transport system
US11412374B2 (en) Aircraft interface device
CN109587821B (en) Aircraft crew connection system and method
US11180255B2 (en) Aircraft seat, aircraft seat arrangement with an aircraft seat and aircraft with an aircraft seat arrangement
CN107484226B (en) Airborne wireless access server
EP3241748A1 (en) Seat module with wireless communication module, vehicle seat with seat module, aircraft and method for operating a seat module
CN109039430A (en) Meet airborne wireless access system, the device and method of a variety of access modules simultaneously
US20160218517A1 (en) Power socket with wireless communication module, vehicle seat with power socket and method for operating a power socket
CA2859868C (en) On-board communication devices for a cab of a vehicle, each with a media server and a radio module by means of which the devices are connected to one another in a wireless fashion
CN110654548A (en) Aircraft seat arrangement and aircraft with an aircraft seat arrangement
EP3499733B1 (en) Method and apparatus for physical security over a powerline connection
US10070372B2 (en) Multi-mode mobile device
US10507740B2 (en) Control device for the comfort equipment of a passenger transport vehicle seat module, seat module and system for controlling comfort equipment
CN210168041U (en) Parallel data chain system of airplane
US11565817B2 (en) Aircraft seat, aircraft seat arrangement having an aircraft seat, and aircraft having an aircraft seat arrangement
US11689278B2 (en) Standardized connection interface between aircraft equipment and a wireless data transmission network external to the aircraft
US20230343224A1 (en) Access-door-integrated wireless intercom system
CN110446182B (en) Airborne communication system
US20210105070A1 (en) Gate-based optical data transmission
CN110572201A (en) Design method and system for parallel data chain system of airplane
CN109752979A (en) A kind of unmanned plane control equipment that can be tracked of video freeze

Legal Events

Date Code Title Description
PB01 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant